EP2815184B1 - Brenner - Google Patents

Brenner Download PDF

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Publication number
EP2815184B1
EP2815184B1 EP13718309.1A EP13718309A EP2815184B1 EP 2815184 B1 EP2815184 B1 EP 2815184B1 EP 13718309 A EP13718309 A EP 13718309A EP 2815184 B1 EP2815184 B1 EP 2815184B1
Authority
EP
European Patent Office
Prior art keywords
section
fuel
swirler
burner
premix
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP13718309.1A
Other languages
English (en)
French (fr)
Other versions
EP2815184A2 (de
Inventor
Mats Andersson
Alessio Bonaldo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP13718309.1A priority Critical patent/EP2815184B1/de
Publication of EP2815184A2 publication Critical patent/EP2815184A2/de
Application granted granted Critical
Publication of EP2815184B1 publication Critical patent/EP2815184B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel

Definitions

  • the invention relates to a burner of a gas turbine extending along an axis and comprising in axial order:
  • flame stabilization at the burner outlet is of high importance to obtain low emission and low combustion dynamics phenomena which can damage the combustor hardware.
  • flow of fuel is delivered through injection nozzles within the burner system and combustion is achieved in the combustion chamber containing a combustion zone.
  • a combustor of that kind is described in patent US 6 152 726 (filing date 28.11.2000 ).
  • the known burner uses several injection channels for fuel supply.
  • gaseous fuel is used e.g. natural gas.
  • a first fuel supply, which is used to inject the main portion of fuel is located in the swirler section, wherein nozzles are provided at the edges of the main swirler vanes.
  • the secondary fuel supply may be located at a central lance, which extends coaxially with the main axis of the burner. This second fuel supply is optional and preferably used to fix the flame front at a specific location and to avoid high frequency fluctuations.
  • a third fuel supply is used to ignite and maintain the flame front in the main combustion zone and located at the end of said outlet section, which comprises an annular rim protruding into said combustion zone, wherein said rim is provided with second fuel nozzles discharging fuel in a radial outward direction.
  • the known burner achieves low emission because most of the fuel is delivered at the swirler vane region which is capable to homogenously distribute the fuel in the airstream respectively to guarantee a good premix.
  • Said central gas injection improves flame stability in a limited range of operation because at higher central gas flow rates the flame position moves an increases combustor dynamics.
  • the third way to inject fuel by said external pilot nozzles improves stability by a diffusive type flame but increases also emissions which also limits the range of operation. At full load conditions the emissions need to be low and therefore the external pilot is fed by only a minor portion of fuel which leads to a smaller pilot flame region which is less effective in stabilizing the main flame.
  • the flow is highly turbulent while a shear layer develops between a high flow speed and regions of decreased flow speed.
  • This shear layer develops between the diffusive flame type of the external pilot and the main combustion zone which reduces the stabilizing effect of the external pilot located at the outer rim of said outlet section for the main combustion zone flame front.
  • the fuel flow of the external pilot has to be increased which results in higher NOX emissions.
  • This effect is further versant by injection of air through mixing tube cooling air holes which reduces the fuel concentration on the shear layer further.
  • the fuel supply to the external pilot must be further increased which does not only increase NOX emissions but also lead to temperatures at the external rim of said outlet section which are not acceptable with regards to material properties of said outlet section.
  • US 2007/0259296 A1 discloses a burner of a gas turbine according to the preamble of claim 1.
  • the dependent claims respectively relate to preferred embodiments of the invention respectively inventive improvements.
  • a burner according to claim 1 is often also referred to as a combustor.
  • Said swirler vanes are designed to increase a circumferential velocity component which leads to a better mixing of fuel and air especially in said mixing section.
  • Said mixing section may be a cylindrical shaped cavity enclosed by an outer shell.
  • the surface of said outer shell may have perforated sections to inject air respectively oxygen containing gas.
  • Said oxygen containing gas is injected in the mixing zone to on the one hand increase the oxygen content of the premix and on the other hand to cool the shell of the mixing section.
  • the cooling film of the air injected prevents the shell to be destroyed by the heat impact from the combustion zone.
  • the outlet section is basically a continuation of the cylindrical shell of the mixing section without perforations for cooling air injection.
  • the downstream end of the outlet section preferably comprises a slight enlargement of the axial cross section of said shell to decrease any turbulence of the flow of the premix entering the combustion zone.
  • said outlet section comprises an annular rim protruding into said combustion zone and being located at a downstream end of said outlet section.
  • the outer surface of said annular rim is provided with second fuel nozzles discharging fuel in an inclined direction between an axial direction and a strictly radial outward direction.
  • the discharged fuel basically forms a conus diverging in axial downstream direction.
  • the burner comprises a central lance extending coaxially in a downstream direction, wherein a downstream tip of said lance is provided with fuel injection nozzles for both gas and oil.
  • FIG. 1 and 2 shows a burner B of a gas turbine according to the invention in a schematic three-dimensional depiction respectively in a longitudinal cross section along a central axis X.
  • Said burner B can be divided along an axial sequence from an upstream end UE to a downstream end DE with regard to the flow of an oxygen containing gas OCG - hereinafter referred to as air A - and the flow of fuel F - gaseous or liquid fuel - a swirler section SW, a mixing section MX, an outlet section OT and a main combustion zone CZ.
  • Said swirler section SW comprises swirler vanes SWV. Leading edges of said swirler vanes SWV can be seen in the three-dimensional depiction of figure 1 .
  • Figure 2 shows schematically the geometry of said swirler vanes SWV and there extension inside said swirler section SW.
  • a main gas supply MGS as well as a central gas supply CGS are part of said swirler section.
  • Said main gas supply MGS supplies a main portion of said fuel F, wherein a flow of fuel F enters channels defined by said swirler vanes SWV from a more radial direction and is deflected into said axial direction.
  • Said central gas supply CGS is designed like a lance extending coaxially in axial direction.
  • nozzles for fuel injection injecting fuel F in an inclined direction between the axial direction and a radial outward direction.
  • Said swirler vanes SWV imprint a circumferential velocity component on the flow to improve mixing of fuel and air in the downstream mixing section MX.
  • Said mixing section MX is defined by a cylindrical shaped shell SG conducting the fuel from said swirler section SW downstream to said outlet section subsequently into said combustion zone CZ.
  • An inner surface of said cylindrical shell SG comprises perforated sections PF for injecting air.
  • the injected air establishes a film covering the inner surface of said shell SG laminary.
  • the injected air A mixes with said fuel F from said swirler section SW resulting in a premix MFOCG of oxygen containing gas OCG and fuel F.
  • Downstream said mixing section MX said premix MFOCG enters said outlet section OT.
  • Said outlet section OT is a cylindrical continuation of said mixing section MX.
  • the inner surface of said outlet section OT is provided with first fuel nozzles FN1 injecting fuel F into said premix MFOCG.
  • Said first fuel nozzles FN1 inject fuel in an inclined direction between a radial inward direction and said axial direction. Generally the direction of injection of said first fuel nozzles can be slightly downstream.
  • the fuel F injected by said first fuel nozzles FN1 enrich said film air A with fuel F before said premix and film air is discharged into said combustion zone CZ.
  • a main flame region MFR of said combustion zone CZ is located with its center on said axis X.
  • a shear layer SL forms between said main flame region MFR of said combustion zone CZ and the downstream end of said outlet section OT. Said downstream end of said outlet section OT protrudes as a rim R into said main combustion zone CZ.
  • An outer surface of said rim R is provided with external pilot fuel nozzles respectively second fuel nozzles FN2 discharging fuel F in a radial outward direction. Said radial outward direction is downstream inclined between said axial direction and said radial outward direction.
  • a diffusion type flame establishes stabilizing a flame front FF in the main flame region MFR.
  • said shear layer SL established is mainly composed of the flow of said air A respectively film air FA from said mixing section MX and said outlet section OT. Since said film air FA is enriched from fuel F discharged by said first fuel nozzles FN1 a flame ignition of said main flame region MFR by said pilot flames is improved.
  • Figure 3 and 4 show respective geometries of inner channels provided in the shell SG of said outlet section OT.
  • a first fuel channel CHF1 for said first fuel nozzle FN1 respectively an inner wall injection point
  • a second fuel channel for said fuel nozzle FN2 respectively an external pilot injector

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Claims (5)

  1. Brenner (B) einer Gasturbine, der sich entlang einer Achse (X) erstreckt und in axialer Reihenfolge das Folgende umfasst:
    - einen Wirblerabschnitt (SW)
    - einen Mischabschnitt (MX)
    - einen Auslassabschnitt (OT)
    - eine Hauptverbrennungszone (CZ)
    - wobei der Wirblerabschnitt (SW) Wirblerflügel (SWV) umfasst, die dazu ausgelegt sind, einen Strom von Brennstoff (F) und Sauerstoff enthaltendem Gas (OCG), der in den Wirblerabschnitt (SW) in einer Umfangsrichtung eindringt, zu verwirbeln,
    - wobei der Mischabschnitt (MX) die Vormischung (MFOCG) aus Brennstoff (F) und Sauerstoff enthaltendem Gas (OCG) zum Auslassabschnitt (OT) leitet,
    - wobei der Auslassabschnitt (OT) die Vormischung (MFOCG) in die Verbrennungszone (CZ) abgibt, wobei die Strömung der Vormischung (MFOCG) von einem kleineren axialen Querschnitt des Mischabschnitts (MX) auf einen größeren Querschnitt der Verbrennungszone (CZ) expandiert wird, so dass Stromlinien der Strömung radial divergieren, wobei eine Oberfläche des Auslassabschnitts (OT), die der Strömung der Vormischung (MFOCG) zugewandt ist, erste Brennstoffdüsen (FN1) aufweist, die Brennstoff in die Vormischung (MFOCG) in einer radial einwärts geneigten Richtung einspritzen, bevor die Strömung der Vormischung (MFOCG) in den Auslassabschnitt (OT) in die Verbrennungszone (CZ) eindringt, dadurch gekennzeichnet, dass der Auslassabschnitt (OT) einen ringförmigen Rand (R) umfasst, der in die Verbrennungszone (CZ) ragt, umfassend zweite Brennstoffdüsen (FN2), die Brennstoff (F) in einer radialen Auswärtsrichtung abgeben.
  2. Brenner (B) nach Anspruch 1,
    wobei die Mischzone (MX) Einlasslöcher (IH) zum Einspritzen von Sauerstoff enthaltendem Gas (OCG) umfasst,
    wobei die Einlasslöcher (IH) dazu ausgelegt sind, einen Film aus Sauerstoff enthaltendem Gas (OCG) entlang der Innenfläche des Mischabschnitts (MX) bereitzustellen.
  3. Brenner (B) nach mindestens einem der Ansprüche 1, 2,
    wobei der Wirblerabschnitt (SW) einen mittige Flüssigbrennstoffeinspritzung (CFI) umfasst, die dazu ausgelegt ist, flüssigen Brennstoff (LF) einzuspritzen.
  4. Brenner (B) nach mindestens einem der Ansprüche 1, 2, 3,
    wobei der Wirblerabschnitt (SW) eine Gasbrennstoffeinspritzung (GFI) umfasst, die Gasbrennstoffeinspritzdüsen (GFN) zum Einspritzen von gasförmigem Brennstoff (GF) als Teil der Wirblerflügel (SWV) umfasst.
  5. Brenner (B) nach mindestens einem der Ansprüche 1, 2, 3, 4
    wobei der Mischabschnitt (MX) eine zylindrische Gestalt aufweist, die sich koaxial entlang der Achse (X) erstreckt.
EP13718309.1A 2012-04-10 2013-04-08 Brenner Not-in-force EP2815184B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13718309.1A EP2815184B1 (de) 2012-04-10 2013-04-08 Brenner

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12163593.2A EP2650612A1 (de) 2012-04-10 2012-04-10 Brenner
PCT/EP2013/057273 WO2013153013A2 (en) 2012-04-10 2013-04-08 Burner
EP13718309.1A EP2815184B1 (de) 2012-04-10 2013-04-08 Brenner

Publications (2)

Publication Number Publication Date
EP2815184A2 EP2815184A2 (de) 2014-12-24
EP2815184B1 true EP2815184B1 (de) 2018-08-29

Family

ID=48182888

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12163593.2A Withdrawn EP2650612A1 (de) 2012-04-10 2012-04-10 Brenner
EP13718309.1A Not-in-force EP2815184B1 (de) 2012-04-10 2013-04-08 Brenner

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP12163593.2A Withdrawn EP2650612A1 (de) 2012-04-10 2012-04-10 Brenner

Country Status (5)

Country Link
US (1) US9664393B2 (de)
EP (2) EP2650612A1 (de)
CN (1) CN104246372B (de)
RU (1) RU2624421C2 (de)
WO (1) WO2013153013A2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3617599A1 (de) 2018-09-03 2020-03-04 Siemens Aktiengesellschaft Brenner mit verbesserter luft-kraftstoff-mischung

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3026346A1 (de) * 2014-11-25 2016-06-01 Alstom Technology Ltd Brennkammerwand
US9927124B2 (en) * 2015-03-26 2018-03-27 Ansaldo Energia Switzerland AG Fuel nozzle for axially staged fuel injection
EP3290804A1 (de) 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Brenner mit kraftstoff- und luftzufuhr in einer wand des brenners
US10690350B2 (en) * 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
US11156362B2 (en) 2016-11-28 2021-10-26 General Electric Company Combustor with axially staged fuel injection
EP3438540A1 (de) * 2017-07-31 2019-02-06 Siemens Aktiengesellschaft Brenner mit einem schalldämpfer
US10907832B2 (en) 2018-06-08 2021-02-02 General Electric Company Pilot nozzle tips for extended lance of combustor burner
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
CN112902171B (zh) * 2021-02-03 2023-07-11 沈阳理工大学 一种双旋燃烧器
US20230003385A1 (en) * 2021-07-02 2023-01-05 General Electric Company Premixer array
US11692711B2 (en) 2021-08-13 2023-07-04 General Electric Company Pilot burner for combustor
CN114738799B (zh) * 2022-04-20 2024-03-26 新奥能源动力科技（上海）有限公司 双燃料燃烧室的头部组件、燃烧室及燃气轮机
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

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GB1031184A (en) * 1964-02-26 1966-06-02 Arthur Henry Lefebvre An improved fuel injection system for gas turbine engines
JP3133066B2 (ja) * 1991-04-25 2001-02-05 シーメンス アクチエンゲゼルシヤフト 石炭ガスおよび別の燃料を有害成分の発生を少なく燃焼するための特にガスタービン用のバーナ燃焼装置
FR2702593B1 (fr) 1993-03-09 1995-04-28 Commissariat Energie Atomique Structure de guidage de particules chargées en électricité.
DE19640198A1 (de) 1996-09-30 1998-04-02 Abb Research Ltd Vormischbrenner
DE19736902A1 (de) * 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
EP0909921B1 (de) * 1997-10-14 2003-01-02 Alstom Brenner für den Betrieb eines Wärmeerzeugers
DE19757189B4 (de) * 1997-12-22 2008-05-08 Alstom Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
EP0931980B1 (de) * 1998-01-23 2003-04-09 ALSTOM (Switzerland) Ltd Brenner für den Betrieb eines Wärmeerzeugers
US6189314B1 (en) 1998-09-01 2001-02-20 Honda Giken Kogyo Kabushiki Kaisha Premix combustor for gas turbine engine
EP0994300B1 (de) 1998-10-14 2003-11-26 ALSTOM (Switzerland) Ltd Brenner für den Betrieb eines Wärmeerzeugers
DE59907942D1 (de) * 1999-07-22 2004-01-15 Alstom Switzerland Ltd Vormischbrenner
CN1316198A (zh) 2000-04-06 2001-10-10 陈治斌 营养阴米粉
EP1389713A1 (de) * 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Stromabwärtiger Pilotringbrenner für Vormischbrenner
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EP2110601A1 (de) * 2008-04-15 2009-10-21 Siemens Aktiengesellschaft Brenner

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3617599A1 (de) 2018-09-03 2020-03-04 Siemens Aktiengesellschaft Brenner mit verbesserter luft-kraftstoff-mischung
WO2020048856A1 (en) 2018-09-03 2020-03-12 Siemens Aktiengesellschaft Burner with improved air-fuel mixing

Also Published As

Publication number Publication date
WO2013153013A3 (en) 2014-04-24
US9664393B2 (en) 2017-05-30
RU2624421C2 (ru) 2017-07-03
US20150082796A1 (en) 2015-03-26
WO2013153013A2 (en) 2013-10-17
RU2014144987A (ru) 2016-06-10
CN104246372A (zh) 2014-12-24
EP2650612A1 (de) 2013-10-16
EP2815184A2 (de) 2014-12-24
CN104246372B (zh) 2016-07-06

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